Encyclopedia Astronautica

N2O4/UDMH propellant rocket stage. Loaded/empty mass 80,000/8,000 kg. Thrust 1,632.80 kN. Vacuum specific impulse 291 seconds.

No Engines: 2.

Status: Design 2000.
Gross mass: 80,000 kg (176,000 lb).
Unfuelled mass: 8,000 kg (17,600 lb).
Height: 27.00 m (88.00 ft).
Diameter: 2.25 m (7.38 ft).
Span: 2.26 m (7.41 ft).
Thrust: 1,632.80 kN (367,068 lbf).
Specific impulse: 291 s.
Specific impulse sea level: 261 s.
Burn time: 125 s.

More... - Chronology...

Associated Countries
Associated Engines
  • YF-20B Beijing Wan Yuan N2O4/UDMH rocket engine. 816.3 kN. In production. Isp=289s. Boosted CZ-2C, CZ-2D, CZ-2E, CZ-2E(A), CZ-3A, CZ-3B, CZ-3C, CZ-4A. First flight 1988. More...

Associated Launch Vehicles
  • CZ-2E(A) Planned upgrade of CZ-2E with enlarged liquid boosters. Probably intended for launch of Chinese space station modules in the 21st century. Fairing was 5.20 m in diameter and 12.39 m long. More...

Associated Propellants
  • N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...

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